26996 Federal Register / Vol. 77, No. 89 / Tuesday, May 8, 2012 / Proposed Rules 

(i) Optional Terminating Action 

Replacing the titanium seat track bolts with 

CRES bolts on both the left and right sides 

of buttock lines 24.75 and 45.50 at Station 

727B, and installing a new splice strap P/N 

146A5342–26, in accordance with the 

Accomplishment Instructions of Boeing 

Special Attention Service Bulletin 737–53– 

1296, dated January 11, 2011, terminates the 

repetitive inspections required by paragraph 

(h) of this AD. 

(j) Alternative Methods of Compliance 

(AMOCs) 

(1) The Manager, Seattle ACO, FAA, has 

the authority to approve AMOCs for this AD, 

if requested using the procedures found in 14 

CFR 39.19. In accordance with 14 CFR 39.19, 

send your request to your principal inspector 

or local Flight Standards District Office, as 

appropriate. If sending information directly 

to the manager of the ACO, send it to the 

attention of the person identified in the 

Related Information section of this AD. 

Information may be emailed to: 9-ANMSeattle-ACO-AMOC-Requests@faa.gov. 

(2) Before using any approved AMOC, 

notify your appropriate principal inspector, 

or lacking a principal inspector, the manager 

of the local flight standards district office/ 

certificate holding district office. 

(3) An AMOC that provides an acceptable 

level of safety may be used for any repair 

required by this AD if it is approved by 

Boeing Commercial Airplanes Organization 

Designation Authorization (ODA) that has 

been authorized by the Manager, Seattle 

ACO, to make those findings. For a repair 

method to be approved, the repair must meet 

the certification basis of the airplane, and the 

approval must specifically refer to this AD. 

(k) Related Information 

(1) For more information about this AD, 

contact Patrick Gillespie, Aerospace 

Engineer, Cabin Safety and Environmental 

Systems Branch, ANM–150S, FAA, Seattle 

Aircraft Certification Office (ACO), 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; phone: 425–917–6429; fax: 425–917– 

6590; email: patrick.gillespie@faa.gov. 

(2) For service information identified in 

this AD, contact Boeing Commercial 

Airplanes, Attention: Data & Services 

Management, P.O. Box 3707, MC 2H–65, 

Seattle, Washington 98124–2207; telephone 

206–544–5000, extension 1; fax 206–766– 

5680; email me.boecom@boeing.com; Internet 

https://www.myboeingfleet.com. You may 

review copies of the referenced service 

information at the FAA, Transport Airplane 

Directorate, 1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, call 

425–227–1221. 

Issued in Renton, Washington, on April 29, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–11019 Filed 5–7–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0427; Directorate 

Identifier 2011–NM–202–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for certain 

Airbus Model A320–214 and-232 

airplanes. This proposed AD was 

prompted by reports that medium-head 

fasteners were installed in lieu of shearhead fasteners on a certain upper panel 

which manufacturer fatigue and damage 

tolerance analyses demonstrated could 

have an affect on panel fatigue life. This 

proposed AD would require repetitive 

inspections for cracking of certain 

fasteners, and repairs if necessary. We 

are proposing this AD to detect and 

correct cracking which could result in 

the loss of structural integrity of the 

airplane. 

DATES: We must receive comments on 

this proposed AD by June 22, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC, between 9 a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

For service information identified in 

this proposed AD, contact Airbus SAS– 

EAW (Airworthiness Office), 1 Rond 

Point Maurice Bellonte, 31707 Blagnac 

Cedex, France; telephone +33 5 61 93 36 

96; fax +33 5 61 93 44 51; email 

account.airworth-eas@airbus.com; 

Internet http://www.airbus.com. You 

may review copies of the referenced 

service information at the FAA, 

Transport Airplane Directorate, 1601 

Lind Avenue SW., Renton, Washington. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1405; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2012–0427; Directorate Identifier 

2011–NM–202–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2011–0176, 

dated September 13, 2011 (referred to 

after this as ‘‘the MCAI’’), to correct an 

unsafe condition for the specified 

products. The MCAI states: 

A problem was reported during the 

installation of upper panels on Frame 35 in 

Airbus A320 final assembly line. 

Investigations revealed that medium head 

fasteners, Part Number (P/N) EN6114V3, 

were installed in lieu of shear head fasteners, 

P/N ASNA2657V3 and ASNA2043V3, which 

were previously used. Installation of these 

medium head fasteners leads to a deeper 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

Federal Register / Vol. 77, No. 89 / Tuesday, May 8, 2012 / Proposed Rules 26997 

countersink in the panel. Fatigue and damage 

tolerance analyses were performed, the 

results of which demonstrated that this 

installation could have a fatigue impact on 

two rows of fasteners between stringers 

(STGR) 5 and 6, and indicated the need for 

a specific inspection in this area. 

This condition, if not detected and 

corrected, could impair the structural 

integrity of the affected aeroplanes. 

For the reasons described above, this 

[EASA] AD requires repetitive special 

detailed [high frequency eddy current] 

inspections [for cracking] of the affected 

fasteners and, depending on findings, the 

accomplishment of associated corrective 

actions [repair]. 

You may obtain further information by 

examining the MCAI in the AD docket. 

Relevant Service Information 

Airbus has issued Service Bulletin 

A320–53–1244, including Appendix 1, 

dated March 17, 2011. The actions 

described in this service information are 

intended to correct the unsafe condition 

identified in the MCAI. 

FAA’s Determination and Requirements 

of This Proposed AD 

This product has been approved by 

the aviation authority of another 

country, and is approved for operation 

in the United States. Pursuant to our 

bilateral agreement with the State of 

Design Authority, we have been notified 

of the unsafe condition described in the 

MCAI and service information 

referenced above. We are proposing this 

AD because we evaluated all pertinent 

information and determined an unsafe 

condition exists and is likely to exist or 

develop on other products of the same 

type design. 

Costs of Compliance 

Based on the service information, we 

estimate that this proposed AD would 

affect about 44 products of U.S. registry. 

We also estimate that it would take 

about 3 work-hours per product to 

comply with the basic requirements of 

this proposed AD. The average labor 

rate is $85 per work-hour. Based on 

these figures, we estimate the cost of the 

proposed AD on U.S. operators to be 

$11,220, or $255 per product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this proposed AD. We have 

no way of determining the number of 

products that may need these actions. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this proposed AD 

would not have federalism implications 

under Executive Order 13132. This 

proposed AD would not have a 

substantial direct effect on the States, on 

the relationship between the national 

Government and the States, or on the 

distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify this proposed regulation: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

We prepared a regulatory evaluation 

of the estimated costs to comply with 

this proposed AD and placed it in the 

AD docket. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

The Proposed Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA proposes to amend 14 CFR part 

39 as follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

2. The FAA amends § 39.13 by adding 

the following new AD: 

Airbus: Docket No. FAA–2012–0427; 

Directorate Identifier 2011–NM–202–AD. 

(a) Comments Due Date 

We must receive comments by June 22, 

2012. 

(b) Affected ADs 

None. 

(c) Applicability 

This AD applies to Airbus Model A320– 

214 and –232 airplanes; certificated in any 

category; manufacturer serial numbers 3456, 

3503, 3516, 3529, 3591, 3597, 3611, 3631, 

3696, 3698, 3714, 3719, 3775, 3777, 3780, 

3782, 3786, 3797, 3805, 3812, 3870, 3907, 

3909, 3913, 3922, 3929, 3946, 3953, 3975, 

3979, 3991, 4010, 4012, 4014, 4027, 4034, 

4043, 4046, 4064, 4065, 4084, 4093, 4094, 

and 4097. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by reports that 

medium-head fasteners were installed in lieu 

of shear-head fasteners on a certain upper 

panel which manufacturer fatigue and 

damage tolerance analyses demonstrated 

could have an effect on panel fatigue life. We 

are issuing this AD to detect and correct 

cracking which could result in the loss of 

structural integrity of the airplane. 

(f) Compliance 

You are responsible for having the actions 

required by this AD performed within the 

compliance times specified, unless the 

actions have already been done. 

(g) Repetitive Inspection 

At the later of the times in paragraphs 

(g)(1) and (g)(2) of this AD: Do a high 

frequency eddy current inspection for 

cracking of the 2 rows of 6 fasteners at frame 

35 between stringers 5 and 6 on the left and 

right sides, in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1244, excluding 

Appendix 1, dated March 17, 2011. Repeat 

the inspection thereafter at intervals not to 

exceed 28,100 flight cycles or 56,300 flight 

hours, whichever occurs first. 

(1) Before the accumulation of 35,900 total 

flight cycles or 88,100 total flight hours, 

whichever occurs first. 

(2) Within 30 days after the effective date 

of this AD. 

(h) Corrective Action 

If any crack is detected during any 

inspection required by paragraph (g) of this 

AD: Before further flight, repair the crack 

using a method approved by either the 

Manager, International Branch, ANM–116, 

Transport Airplane Directorate, FAA; or the 

European Aviation Safety Agency (EASA) or 

its delegated agent. 

(i) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

mstockstill on DSK4VPTVN1PROD with PROPOSALS

26998 Federal Register / Vol. 77, No. 89 / Tuesday, May 8, 2012 / Proposed Rules 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, Washington 98057– 

3356; telephone (425) 227–1405; fax (425) 

227–1149. Information may be emailed to: 

9-ANM-116-AMOC-REQUESTS@faa.gov. 

Before using any approved AMOC, notify 

your appropriate principal inspector, or 

lacking a principal inspector, the manager of 

the local flight standards district office/ 

certificate holding district office. The AMOC 

approval letter must specifically reference 

this AD. 

(2) Airworthy Product: For any requirement 

in this AD to obtain corrective actions from 

a manufacturer or other source, use these 

actions if they are FAA-approved. Corrective 

actions are considered FAA-approved if they 

are approved by the State of Design Authority 

(or their delegated agent). You are required 

to assure the product is airworthy before it 

is returned to service. 

(j) Related Information 

Refer to MCAI EASA Airworthiness 

Directive 2011–0176, dated September 13, 

2011; and Airbus Service Bulletin A320–53– 

1244, excluding Appendix 1, dated March 

17, 2011; for related information. 

Issued in Renton, Washington, on April 29, 

2012. 

Michael Kaszycki, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2012–11023 Filed 5–7–12; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2012–0428; Directorate 

Identifier 2011–NM–078–AD] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), DOT. 

ACTION: Notice of proposed rulemaking 

(NPRM). 

SUMMARY: We propose to adopt a new 

airworthiness directive (AD) for all 

Airbus Model A330–243, –243F, –342, 

and –343 airplanes. This proposed AD 

was prompted by reports of cracking of 

air intake cowls on Rolls-Royce Trent 

engines, worn and detached attachment 

links, and fractured thermal anti-ice 

(TAI) piccolo tubes. This proposed AD 

would require inspecting piccolo tubes, 

piccolo tube mount links, the aft side of 

the forward bulkhead, and outer 

boundary angles (OBA) for cracks, 

fractures, and broken links, and 

corrective actions if necessary. We are 

proposing this AD to prevent degraded 

structural integrity of the engine nose 

cowl and a broken piccolo tube, which 

could lead to in-flight damage of the 

engine and reduced thermal anti-ice 

performance. 

DATES: We must receive comments on 

this proposed AD by June 22, 2012. 

ADDRESSES: You may send comments by 

any of the following methods: 

• Federal eRulemaking Portal: Go to 

http://www.regulations.gov. Follow the 

instructions for submitting comments. 

• Fax: (202) 493–2251. 

• Mail: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC 20590. 

• Hand Delivery: U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC, between 9 

a.m. and 

5 p.m., Monday through Friday, except 

Federal holidays. 

For Airbus service information 

identified in this proposed AD, contact 

Airbus SAS—Airworthiness Office— 

EAL, 1 Rond Point Maurice Bellonte, 

31707 Blagnac Cedex, France; telephone 

+33 5 61 93 36 96; fax +33 5 61 93 45 

80; email airworthiness.A330- 

A340@airbus.com; Internet http:// 

www.airbus.com. For Rolls-Royce 

service information identified in this 

proposed AD, contact Rolls-Royce Plc, 

Technical Publications, P.O. Box 31, 

Derby, DE24 8BJ, United Kingdom; 

telephone 44 (0) 1332 245882; fax 44 (0) 

1332 249936; Internet http://www.RollsRoyce.com. You may review copies of 

the referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, 

Washington. For information on the 

availability of this material at the FAA, 

call 425–227–1221. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov; or in person at the 

Docket Operations office between 9 a.m. 

and 5 p.m., Monday through Friday, 

except Federal holidays. The AD docket 

contains this proposed AD, the 

regulatory evaluation, any comments 

received, and other information. The 

street address for the Docket Operations 

office (telephone (800) 647–5527) is in 

the ADDRESSES section. Comments will 

be available in the AD docket shortly 

after receipt. 

FOR FURTHER INFORMATION CONTACT: 

Vladimir Ulyanov, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, 

Washington 98057–3356; telephone 

(425) 227–1138; fax (425) 227–1149. 

SUPPLEMENTARY INFORMATION: 

Comments Invited 

We invite you to send any written 

relevant data, views, or arguments about 

this proposed AD. Send your comments 

to an address listed under the 

ADDRESSES section. Include ‘‘Docket No. 

FAA–2012–0428; Directorate Identifier 

2011–NM–078–AD’’ at the beginning of 

your comments. We specifically invite 

comments on the overall regulatory, 

economic, environmental, and energy 

aspects of this proposed AD. We will 

consider all comments received by the 

closing date and may amend this 

proposed AD based on those comments. 

We will post all comments we 

receive, without change, to http:// 

www.regulations.gov, including any 

personal information you provide. We 

will also post a report summarizing each 

substantive verbal contact we receive 

about this proposed AD. 

Discussion 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Community, has issued EASA 

Airworthiness Directive 2011–0062, 

dated April 4, 2011 (referred to after this 

as ‘‘the MCAI’’), to correct an unsafe 

condition for the specified products. 

The MCAI states: 

During shop visit, several primary 

assembly structures of A330 aeroplanes Trent 

700 [engine] air intake cowl have been found 

with cracks in the forward bulkhead web, 

web stiffeners and outer boundary angles. 

Several attachment links have been found 

severely worn, and some had become 

detached. In 2 cases, the Thermal Anti Ice 

(TAI) Piccolo tube was found fractured. 

Investigations are still ongoing to determine 

the root cause(s). 

If not detected and corrected, a broken 

Piccolo tube in conjunction with forward 

bulkhead damage could ultimately lead to in 

flight detachment of the outer barrel, which 

would constitute an unsafe condition. 

For the reasons described above, this [EASA] 

AD requires to perform inspections of RR 

[Rolls-Royce] Trent 700 [engine] nose cowls 

and, depending on findings, to do the 

applicable corrective action(s). These 

inspections include internal inspection of 

Piccolo tube, detailed inspection of Piccolo 

mstockstill on DSK4VPTVN1PROD with PROPOSALS